Projectile



P. E. J. DENOIX PROJECTILE Filed June 28, 1958 T Y T FF 2 Q UNITEDSTATES PROJECTILE Paul Emile Joseph Denoi x, Paris, France, assignor toSageb, Socit Anonyme. dc Gestion ct dExploitation de Brevets, Fribourg,Switzerland, a corporation of Switzerland Application June 2a, 1933,Serial No. 216,406 In Lnxemburg June 28, 1937 3 Claims. (Cl. I 223) Thisinventionrelates to projectiles comprisfeet of further strengthening theconcentration ing a. reaction propulsion device. of the mass in themidway portion.

Shells enclosing a reaction propulsion charge The forward portion of thecomplete projectile which discharges either into a central nozzle or mayadvantageously comprise a point having an 35 into lateral nozzles havealready been proposed. inflected curve, of the type described in my cor-5 The nozzles may be directed parallel to the ion-- responding U. S.patent application 192,411 filed gitudinal axis of the shell, in whichcase the reon February 24,1938. action eflect imparts thereto only anaccelera- The shell may be fired with the aid of a weak tion oftranslation; particularly when they are initial firing charge, impartingonly a minimum disposed on the periphery of the projectile, said ofreaction to the apparatus. The latter can 10 nozzles may also beinclined relatively to the thus be mounted without inconvenience on anaxial plane of the shell, with a view to having at v aircraft, whichwill be able to discharge bomb the same time the eifect of increasing orreducing projectiles, at great distances, at the objectives its velocityof gyration. that it desires to hit. it The projectiles of the presentinvention are Further features and advantages of the invencharacterisedin that the lateral propulsive noztion" will become apparent from thefollowing zles, with which they are provided, are disposed descriptiontaken in conjunction with the acnear or slightly in front of the centreof gravity companying drawing which illustrates diagram-' of the chargedprojectile. matically and by way of example, various em By virtue ofthis arrangement, the stability of bodiments thereof and in which: 20the projectile cannot be affected in any appre- Figure 1 is an axialsection of one form of the ciable manner by a defect of symmetry in theinvention. thrusts applied by the nozzleadue, for example, Figure 2 isan axial section of a modified form to an irregularity in theirdischarge or to imof the invention. 2 perfect centering. In theembodiment shown in Fig. 1, the com- According to another feature of theinvention, plete shell consists of an outer casing, in which thecomplete shell is constituted by a casing or is centred an internalshell I, cyllndro-ogival in body of optimum aerodynamic or streamlineshape and disposed near the centre of gravity shape enclosing aprojectile of any desired G of the complete charged shell. The casing isshape, and, if desired, an ordinary projectile of streamline shape andhas the greatest part 30 suitably immobilised and centred near thecentre of its longitudinal exterior profile in the form of of gravity ofthe whole arrangement. a tip decreasing from the portion of maximum Inone embodiment, the centering of the indiameter of the casing to thefront end thereof. ternal projectile is efiected, in whole or in part,The casing comprises a base 2 fixed on a nozzlewith the aid of thenozzle-carrier member, on carrier ring 3, which serves at the same timefor 35 which the internal projectile is fastened by any centering theshell I. The lateral nozzles l, 5 are suitable means. In the case of anexplosion prosituated substantially at the height of the centre jectile,this arrangement promotes the destrucof gravity G. The forward portion 6of the castion of the nozzle-carrier member and ensures its ing haspreferably an inflected curve, in order embacious utilisation on impact,when explosion to facilitate the penetration of the air, as deoccurs.scribed in the aforesaid specification No. 192,- 40

According to a further feature of the .inven- 411. tion, the front andrear portions of the casing The compartments 1 and 8 bounded by the holdreactive charges which discharge into the casing in front of and behindthe shell i hold nozzles placed level with or in front of the centre areaction charge. The rear charge discharges 45 of gravity. 7 into thenozzles 5 and the front charge into the This concentration of the massof the entire nozzles t. projectile on its periphery and near the centreThe ofl'ensive charge 9 enclosed in the shell i of gravity enablesexcellent stability to be 010- is insulated from its walls by means of alayer tained and retained during the trajectory, despite Ill of suitableheat-insulating material. 50 the reduction in weight of the projectileunder The ofiensive charge 9 is primed with the aid the effect of thecombustion of the reaction of a percussion device ll connected by afiring charge, since, when two propulsive charges are tube I 2to a fuzel3. employed, this reduction in'weight takes place The shell may,furthermore, contain a base at the two ends of the projectile and hasthe effuze M. C 55 The rear reaction charge is brought into operationwith the aid of Y an ignition fuze l5 or any other suitable device. Asimilar fuze, preferably placed at Ila ignites the reaction charge inthe compartment 1.

These fuzes are regulated so as to bring the reaction charges operationat the desired moment, during the trajectory or on departure of theshot.

ll denotes a driving banddisposed on the base of the casing 2, and I8 adiscardable centering band mounted on the nozzle-carrier ring 3. Theprojectile ends at the front in a tapered point IS, the outer surface ofwhich prolongs the inflected curve of the portion 6 of the casing.

Fig. 2 shows a modification of the projectile shown in Fig. 1, fromwhich it differs in that the internal shell I, instead of itself havinga screwthread coming into engagement with a thread on the nozzle-carriermember 3, is in contact with the latter only through shoulders 51engaging assembly screws 58. The external side walls of the shell Istand a slight distance away from the internal walls of the member 3, inorder to permit the gases free access to the nozzles l, 5 placed nearthe centre of gravity G.

In shells such as that shown in Fig. 1, comprising a propulsive chargeat the front and another at the rear, the position of the centre ofgravity of the whole projectile remains practically immovable throughoutthe trajectory, the projectile being lightened at both ends 'inproportion as the combustion of the reactive charges proceeds.

It is to be clearly understood that minor changes in the details ofconstruction and arrangement of parts may be made without departing fromthe scope of the invention as set forth in the appended claims.

I claim:

L A projectile comprising an outer casing of streamline/shape, a nozzlecarrying member disposed on the casing in the vicinity of the center ofgravity of the' projectile and being provided with nozzles, an innercasing separate from said outer casing and centered in said nozzlecarrying member and completely enclosed within said outer casing andspaced therefrom, said inner. casin'g having an oifensive charge thereinand forming an internal shell, and a propulsive rocket charge in thespace provided between said outer casing and said inner casing and indischarge communication with said nozzles.

2. A projectile comprising a casing having the greatest part of .itslongitudinal exterior profile in the form of a tip decreasing from theportion of maximum diameter of the casing to the front end thereof, anozzle carrying member disposed on the casing in the vicinity'of thecenter of gravity of the projectile, said nozzle carrying memher beingprovided with nozzles, a shell centered in said nozzle carrying memberand completely enclosed within said casing, a bursting charge in saidshell, and a propulsive rocket charge in said casing and in dischargecommunication with said nozzles.

3. A projectile comprising a casing having the greatest part of itslongitudinal exterior profile in the'form of a tip decreasing from theportion of maximum diameter of the casing to the front end thereof, anozzle carrying member fixed in said casing in the vicinity of thecenter of gravity of the projectile, said nozzle carrying member beingformed with a front and rear series of nozzles, a shell centered in saidnozzle carrying member and completely enclosed within said casing, abursting charge in said shell, a front rocket charge in said casing infront of said shell, 2. rear rocket charge in said casing in rear ofsaid shell, said front and rear rocket charges being in dischargecommunication with said front and rear series of nozzles respectively.

PAUL EMILE JOSEPH DENOIX.

